1 Turbine Engine © Devinder K Yadav
Aerospace Propulsion Study For Shenyang Aerospace University by Lale420 (Final_Eaxm_2 ) )
Apr 12, 2017
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1
Turbine Engine
© Devinder K Yadav
2
Gas Turbine Fuels
Liquid hydrocarbons similar to kerosene
Some are blended with gasoline
Narrow cut/wide cut
Jet fuels are not color coded but may have
a natural pale straw colour
3
Jet Fuel Qualities
Ease of flow
able to start readily but not be volatile
complete and rapid combustion
high calorific value
non-corrosive
lubricating
minimal fire hazard 4
Jet Fuel Types (AVTUR)
Jet A – no gasoline blend
Jet A1 – similar to Jet A but with a lower
freezing point (also called JP-8* or F34)
Jet B – contains a gasoline blend, higher
flammability, generally for cold climates
*JP-8 has additional additives
JP-5, JP-8 - Military fuels
5
Some Fuel Comparisons
Flash point Avtur +38oC
Avgas –400C
Volatility Avtur lower than Avgas
Avtur harbours more dissolved water
which can freeze, produce waxes and allow
microbiological growth 6
Some Fuel Comparisons
7
Jet Fuel Additives
The most common fuel additives are the
anti-icing and anti-microbiocidal agents
Anti-icing additives keep entrained water
from freezing
Microbiocidal agents kill microbes fungi
and bacteria which form a slime and in
some cases a matted waste in fuel systems 8
Fungus and bacteria grown in diesel/water
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Jet Fuel Additives
Reduces the freezing point of any water
present.
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Water Detection in Turbine Fuel
All aviation fuels can contain some
dissolved water
Turbine fuel more so than gasoline
CAO 20.2 Subsection 5
11
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Fuel Heat Content
Specific gravity Avgas 0.7 approx
Avtur 0.8 approx
Avtur yields more heat than Avgas per
unit volume
Avgas yields more heat than Avtur per unit
weight 13
Fuel Control
The purpose of the fuel control unit is to
maintain a correct combustion zone air-to-
fuel mixture ratio of 15:1 by weight
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Fuel Control
To maintain the correct air-to-fuel
relationship altitude, air temperature and
aircraft speed must be considered
These variables change the density of the
air at the engine intake and consequently
the mass of air induced through the engine
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Fuel Control
Many signals are sent to the fuel control unit
to maintain the correct fuel-to-air ratio
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Fuel Control
Engine speed (N2)
Used for both steady state fuel
scheduling and acceleration/deceleration
fuel scheduling
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Fuel Control
Inlet Pressure (Pt2)
A total pressure signal from a probe
in the engine inlet
The pressure will be the result of
aircraft speed, altitude and ram
conditions 18
Fuel Control
Compressor Discharge Pressure (PS3)
Static pressure signal of the mass
airflow at that point in the engine
19
Fuel Control
Burner Can Pressure (PS4)
A static pressure signal from within
the combustion liner
The quick response this signal gives
makes it valuable in preventing stalls,
flameouts and over-temperature
conditions 20
Fuel Control
Inlet Temperature (Tt2)
A total temperature (actual plus
ram) signal from the inlet
This signal provides the control with
an airflow density value against which
a fuel schedule can be established
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Fuel Control
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1
Turbine Engine
2
Turbine Engine Lubrication System
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Turbine Engine Lubrication System
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Dry Sump Lubrication System
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Dry Sump Lubrication System
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Wet Sump Lubrication System
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Oil Pump
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Oil Seals
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Fuel cooled oil cooler (FCOC)
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Fuel cooled oil cooler (FCOC)
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1
Turbine Engine
2
Engine air bleed and internal cooling System
3
Engine air bleed and internal cooling System
4
Engine air bleed and internal cooling System
5
Engine air bleed and internal cooling System
6
Engine air bleed and internal cooling System
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8
9
10
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Bleed Air Systems
Bleed air is tapped from various
compressor stages for use in the engine and
aircraft
Bleed air is typically 4 – 5% of total engine
airflow
A reduction in engine airflow results in a
reduction in engine performance
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Bleed Air Systems
13
Bleed Air Systems
internal sealing
14
Oil Seals
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Bleed Air Systems
Internal cooling
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Bleed Air Systems
Internal cooling
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Bleed Air Systems
Internal cooling
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Bleed Air Systems Internal cooling
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Bleed Air Systems
external cooling & sealing
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Engine Anti-ice System
• The engine anti-ice system uses engine bleed air to provide engine cowl inlet ice protection. •The system can be operated in-flight or on ground. •The left and right engines have identical, independent anti-ice systems. This allows the remaining system to operate, if one engine fails.
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Bleed
Air
Systems
engine
anti ice
22
Bleed
Air
Systems
engine
anti ice
23
Engine Anti-ice System
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